US20240085022A1 - Gas turbine combustor - Google Patents

Gas turbine combustor Download PDF

Info

Publication number
US20240085022A1
US20240085022A1 US18/518,811 US202318518811A US2024085022A1 US 20240085022 A1 US20240085022 A1 US 20240085022A1 US 202318518811 A US202318518811 A US 202318518811A US 2024085022 A1 US2024085022 A1 US 2024085022A1
Authority
US
United States
Prior art keywords
fuel injection
fuel
stepped recess
combustion
air guide
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
US18/518,811
Other languages
English (en)
Inventor
Daniel KRONIGER
Atsushi Horikawa
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Kawasaki Motors Ltd
Original Assignee
Kawasaki Jukogyo KK
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Kawasaki Jukogyo KK filed Critical Kawasaki Jukogyo KK
Publication of US20240085022A1 publication Critical patent/US20240085022A1/en
Assigned to KAWASAKI JUKOGYO KABUSHIKI KAISHA reassignment KAWASAKI JUKOGYO KABUSHIKI KAISHA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HORIKAWA, ATSUSHI, KRONIGER, Daniel
Pending legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/70—Baffles or like flow-disturbing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices

Definitions

  • the present invention relates to a combustor used in a gas turbine engine.
  • a combustor for achieving low-NOx combustion and backfire prevention while using high-reactivity gas such as hydrogen as fuel
  • a combustor that uses a fuel injection device configured such that a plurality of annular members for injecting fuel are arranged concentrically, the fuel is injected in a dispersed manner in radial directions from multiple fuel injection holes provided in each annular member, and air flows toward the combustion chamber side in a direction substantially perpendicular to the fuel injected from each fuel injection hole (see, for example, Patent Document 1).
  • the combustor having such a structure, occurrence of local high-temperature combustion is suppressed by multipoint dispersed injection of the fuel, whereby low-NOx combustion is achieved. Further, to the injected fuel, air is supplied toward the combustion chamber side, whereby occurrence of a backfire phenomenon is suppressed.
  • an object of the present invention is to make it possible to stably maintain a flame even in a case of using fuel having comparatively low reactivity in a combustor of a multipoint injection type that can achieve low-NOx combustion and backfire prevention.
  • a gas turbine combustor includes: a combustion tube forming a combustion chamber on an inner side; and a fuel injection device provided at a top portion of the combustion tube and configured to inject fuel into the combustion chamber.
  • the fuel injection device includes a fuel injection portion having a plurality of fuel injection holes each configured to inject the fuel in a direction containing a component perpendicular to an axial direction of the combustion chamber, and a common fuel supply chamber configured to supply the fuel into the plurality of fuel injection holes, and an air guide portion having an air guide groove configured to guide air for combustion to the fuel injected from each fuel injection hole.
  • the fuel injection portion has an air guide surface configured to guide the air for combustion and located frontward in the axial direction of the combustion chamber relative to the fuel injection hole.
  • a fuel injection opening of the fuel injection hole is provided at a bottom wall surface of a stepped recess recessed in a step shape from the air guide surface.
  • the stepped recess is provided to the fuel injection portion and the fuel injection opening of the fuel injection hole is formed at the bottom wall surface of the stepped recess, whereby it becomes possible to stably maintain a flame even in a case of using fuel having low reactivity, as described in detail later.
  • FIG. 1 is a block diagram showing a schematic configuration of a gas turbine engine to which a combustor according to an embodiment of the present invention is applied;
  • FIG. 2 is a partially cutaway perspective view showing the combustor according to the embodiment of the present invention.
  • FIG. 3 is a front view showing an example of a fuel injection device used in the combustor in FIG. 2 ;
  • FIG. 4 is a partially enlarged front view showing the fuel injection device in FIG. 3 ;
  • FIG. 5 is a partially enlarged vertical sectional view showing the fuel injection device in FIG. 3 ;
  • FIG. 6 is a front view showing another example of the fuel injection device used in the combustor in FIG. 2 ;
  • FIG. 7 is a partially enlarged perspective view showing the fuel injection device in FIG. 3 ;
  • FIG. 8 is a partially enlarged plan view showing the fuel injection device in FIG. 3 ;
  • FIG. 9 shows a result of CFD combustion analysis on the fuel injection device used in the combustor in FIG. 2 .
  • FIG. 1 shows a schematic configuration of a gas turbine engine (hereinafter, simply referred to as gas turbine) GT to which a combustor according to an embodiment of the present invention is applied.
  • the gas turbine GT is configured such that introduced air is compressed by a compressor 1 and led to a combustor 3 , fuel is injected into the combustor 3 and combusted, and a turbine 5 is driven by obtained high-temperature and high-pressure combustion gas G.
  • the turbine 5 is connected to the compressor 1 via a rotary shaft 7 , and the compressor 1 is driven by the turbine 5 .
  • a load L such as a rotor of an aircraft or an electric generator is driven.
  • the combustor 3 is a combustor of a can type in which a plurality of combustor cans are annularly arranged around the axis of the gas turbine GT, for example.
  • the type of the combustor 3 is not limited to the can type, and may be an annular type, for example.
  • the combustor 3 includes a combustion tube 11 forming a combustion chamber 9 on the inner side, and a fuel injection device 13 which is attached to a top portion (most-upstream portion) 13 a of the combustion tube 11 and injects fuel and air into the combustion chamber 9 .
  • the fuel injected from the fuel injection device 13 is ignited by an igniter P provided to the combustion tube 11 , whereby a flame is formed in the combustion chamber 9 .
  • the combustion tube 11 and the fuel injection device 13 are stored concentrically in a substantially cylindrical housing H serving as an outer tube of the combustor 3 .
  • a substantially cylindrical housing H serving as an outer tube of the combustor 3 .
  • the combustion chamber 9 side along an axial direction C of the combustion chamber 9 is referred to as “rear side”, and the opposite side is referred to as “front side”.
  • the axial direction C of the combustion chamber 9 is simply referred to as “axial direction C”.
  • the combustor 3 is configured as a reverse-flow type in which the flowing directions of air A and the combustion gas G are opposite to each other. That is, the combustor 3 has an air introduction passage 17 formed between the housing H, and the combustion tube 11 and a support tube 15 extending in a tubular shape frontward from the combustion tube 11 . Through the air introduction passage 17 , the air A compressed by the compressor 1 ( FIG. 1 ) is led in the direction opposite to the flowing direction of the combustion gas G in the combustion chamber 9 .
  • the combustor 3 may be an axial-flow type in which the flowing directions of the air A and the combustion gas G are the same.
  • a plurality of air introduction holes 19 are provided so as to be arranged in the circumferential direction.
  • the air A sent through the air introduction passage 17 passes the air introduction holes 19 , to be introduced into an air supply passage 21 formed inside the support tube 15 , and then the air A is sent toward the fuel injection device 13 on the rear side.
  • the fuel injection device 13 includes a fuel injection portion 23 and an air guide portion 25 .
  • the fuel injection portion 23 and the air guide portion 25 are each formed in an annular shape.
  • a plurality of (in the shown example, four) fuel injection portions 23 having different diameter sizes are arranged concentrically with each other and concentrically with the combustor 3 ( FIG. 2 ), and annular air guide portions 25 corresponding to the shapes of the respective fuel injectors are arranged on the inner circumferential side and the outer circumferential side of each fuel injection portion 23 .
  • the fuel is supplied to each fuel injection portion 23 of the fuel injection device 13 via a fuel supply passage 27 ( FIG. 2 ).
  • the fuel injection portion 23 has a plurality of fuel injection holes 29 for injecting fuel, and a common fuel supply chamber 31 for supplying the fuel F to the plurality of fuel injection holes 29 .
  • each fuel injection hole 29 is formed so as to inject fuel in a direction containing a component perpendicular to the axial direction C.
  • each fuel injection hole 29 is formed so as to inject the fuel F in a direction (in this example, a radial direction R of the annular fuel injection portion 23 ) perpendicular to the axial direction C.
  • a vertical cross-section of the fuel injection portion 23 has a rectangular shape in the entirety, and the fuel injection holes 29 are formed as holes that open at a wall surface facing outward in the radial direction R of the fuel injection portion 23 and/or a wall surface facing inward in the radial direction R.
  • the air guide portion 25 has air guide grooves 33 which guide the air A for combustion to the respective fuel injection holes 29 .
  • the air guide portion 25 is formed as a plate-shaped member in a direction parallel to a plane perpendicular to the axial direction C and is located on the front side relative to the fuel injection hole 29 of the fuel injection portion 23 (i.e., on the upstream side in the flowing direction of the air A).
  • the air guide portion 25 provided as described above is partially cut out in an area on the fuel injection portion 23 side as shown in FIG. 4 , whereby the air guide grooves 33 are formed.
  • one air guide groove 33 is provided per one fuel injection hole 29 .
  • the fuel F injected from each fuel injection hole 29 of the fuel injection portion 23 is premixed with the air A guided by the air guide groove 33 of the air guide portion and then is injected as premixed gas into the combustion chamber 9 .
  • the air guide portion 25 the air A from the upstream side is guided in the axial direction C to the fuel F injected from each fuel injection hole 29 , whereby the fuel F and the air A cross in directions substantially perpendicular to each other.
  • the fuel F and the air A can be uniformly mixed outside the fuel injection device 13 .
  • the injection direction of the fuel F from the fuel injection hole 29 of the fuel injection portion 23 may be any direction that contains a component perpendicular to the axial direction C, and may be tilted in the axial direction C within a range of ⁇ 10° relative to the direction perpendicular to the axial direction C, for example.
  • the entire configuration of the fuel injection device 13 is not limited to the above example.
  • the shape of the fuel injection portion 23 is not limited to the annular shape shown in FIG. 3 , and may be a rectangular shape in a front view (as seen in the axial direction C of the combustion chamber 9 ), as in a modification shown in FIG. 6 . It is not necessary to provide a plurality of the fuel injection portions 23 and a plurality of the air guide portions 25 corresponding thereto, and one fuel injection portion 23 and one air guide portion may be provided.
  • the fuel injection portion 23 has an air guide surface 35 which guides the air A, on the front side relative to the fuel injection hole 29 .
  • the air guide surface 35 is formed as a flat surface extending in parallel to the axial direction C.
  • a stepped recess 37 recessed in a step shape from the air guide surface 35 is formed.
  • the stepped recess 37 extends to the rear end of the fuel injection portion 23 .
  • a fuel injection opening 29 a of the fuel injection hole 29 is formed at a bottom wall surface 39 of the stepped recess 37 .
  • a direction toward the bottom wall side of the stepped recess 37 may be referred to as “downward direction”, and a direction toward the air guide surface 35 side may be referred to as “upward direction”.
  • the stepped recess 37 is formed in a shape recessed with a plurality of stages (in this example, two stages), and has the bottom wall surface 39 at the lowermost stage and a bottom wall surface 40 at the first stage.
  • the fuel injection opening 29 a of the fuel injection hole 29 is formed at the bottom wall surface 39 at the lowermost stage.
  • the fuel injection opening 29 a of the fuel injection hole 29 is formed at the bottom wall surface 40 at the first stage.
  • the lowermost stage part of the stepped recess 37 may be referred to as first step portion 37 a
  • a second stage part may be referred to as second step portion 37 b.
  • both side walls 41 of the stepped recess 37 are formed in such a shape that the interval between both side walls 41 gradually expands from the front end of the stepped recess 37 toward the rear end thereof (i.e., toward the combustion chamber 9 side). More specifically, as shown in FIG. 8 , both side walls 41 of the stepped recess 37 extend so as to form parts of two equal-length sides of a virtual isosceles triangle whose bottom side is the rear end of the fuel injection portion in a plan view. In the shown example, a front end portion 43 of the stepped recess 37 , corresponding to the apex of the virtual isosceles triangle, is formed in a curved shape recessed frontward.
  • both side walls 41 of the stepped recess 37 By forming both side walls 41 of the stepped recess 37 in such a shape that the interval between both side walls 41 gradually expands from the front end toward the rear end as described above, the flow speed of mixture gas flow of the air A and the fuel F injected from the fuel injection hole 29 gradually decreases through expansion of the flow path as the mixture gas moves toward the combustion chamber 9 side.
  • the flow speed of flow of the fuel F injected from the fuel injection hole 29 gradually decreases through expansion of the flow path as the fuel F moves upward. Thus, mixing of the fuel F and the air A is further promoted.
  • the range of an angle ⁇ formed by both side walls 41 is preferably 0° ⁇ 80°, more preferably 20° ⁇ 60°, and even more preferably 25° ⁇ 40°.
  • angles ⁇ 1 , ⁇ 2 between the side walls 41 at the respective stages in the multistage stepped recess 37 are the same a, but in the case where the stepped recess 37 has a plurality of stages, the angles between the side walls 41 at the respective stages may be different from each other.
  • both side walls 41 of the stepped recess 37 it is not necessary to form both side walls 41 of the stepped recess 37 in such a shape that the interval between both side walls 41 gradually expands from the front end toward the rear end as described above, and a may be 0° or may be a negative angle (such an angle that the interval between both side walls 41 gradually narrows from the front end toward the rear end).
  • the shapes of the both side walls 41 need not be straight shapes as shown in the drawings, and may be curved, for example.
  • the stepped recess 37 has a plurality of stages, and the stepped recess 37 may have only one stage. In a case where the stepped recess 37 has a plurality of stages, the number of stages is not limited to two as shown in the drawings, and may be three or more.
  • the position of the fuel injection opening 29 a of the fuel injection hole 29 in the bottom wall surface 39 at the lowermost stage of the stepped recess 37 is not particularly limited. However, as described later, it has been confirmed that a flame can be more stably maintained when a distance D between a center point O of the fuel injection opening 29 a of the fuel injection hole 29 and the front end point at the lowermost stage of the stepped recess 37 is shorter. The reason is considered that the effects (1) to (3) by the stepped recess 37 as described above are obtained more significantly when the fuel injection hole 29 is close to the rear end wall of the stepped recess 37 .
  • the position of the stepped recess 37 relative to the air guide portion is not particularly limited. However, the flow speed of the air A for combustion is greatest near the air guide groove 33 of the air guide portion 25 , and therefore the fuel F is preferably injected near the air guide groove 33 . In addition, from the standpoint for backfire prevention, entry of the fuel F into the air A is preferably performed on the downstream side of the air guide portion 25 . From this standpoint, the front end of the stepped recess 37 is preferably located rearward relative to the front end of the air guide portion 25 .
  • the front end of the stepped recess 37 is preferably located within the range of the thickness (the dimension in the axial direction C) of the air guide portion 25 , and the front end of the stepped recess 37 more preferably coincides with the center position of the thickness of the air guide portion 25 .
  • the entirety of the stepped recess 37 is preferably included within the width-direction range of the air guide groove 33 .
  • each part of the stepped recess 37 are selected as appropriate in accordance with the specifications such as the output, the size, and fuel F to be used, required for the combustor 3 .
  • the hole diameter d of the fuel injection hole 29 may be approximately 0.5 mm to 1.0 mm in the case of the fuel injection hole 29 for multipoint injection as described above.
  • the dimension in the axial direction C and the dimension in the width direction of the stepped recess 37 may be approximately several mm.
  • a distance c from the center point O of the fuel injection opening 29 a of the fuel injection hole 29 to the rear end of the bottom wall surface 39 of the first step portion 37 a may be not less than 1.5 mm and not greater than 4.0 mm.
  • a height h 1 of the first step portion 37 a may be not less than 0.1 mm and not greater than 1.5 mm, and a height h 2 of the second step portion 37 b may be not less than 0.2 mm and not greater than 3.0 mm.
  • a distance D 1 from the center point O of the fuel injection opening 29 a of the fuel injection hole 29 to the front end point of the first step portion 37 a may be not less than 0.2 mm and not greater than 1.9 mm, and a similar distance D 2 for the second step portion 37 b may be not less than 0.4 mm and not greater than 2.6 mm.
  • a curvature radius r 1 of a curved part at the front end of the first step portion 37 a may be not less than 0.2 mm and not greater than 1.5 mm, and a similar curvature radius r 2 for the second step portion 37 b may be not less than 0.6 mm and not greater than 2.0 mm.
  • a conventional fuel injection device not having the stepped recess 37 was used as Comparative example, and the fuel injection device 13 shown in FIG. 7 was used as Example.
  • hydro fuel fuel of 100% hydrogen gas
  • the kind of fuel F used in the combustor 3 according to the present embodiment is not particularly limited. However, as described above, by providing the stepped recess 37 to the fuel injection portion 23 , flame maintaining performance is particularly significantly improved for fuel F having lower reactivity than hydrogen gas. Therefore, for example, by using the mixture fuel of hydrogen gas and natural gas used in the above CFD combustion analysis, it is possible to ensure stable operation while reducing fuel cost.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
US18/518,811 2021-05-28 2023-11-24 Gas turbine combustor Pending US20240085022A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
JP2021090376 2021-05-28
JP2021-090376 2021-05-28
PCT/JP2022/020623 WO2022249938A1 (ja) 2021-05-28 2022-05-18 ガスタービン燃焼器

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2022/020623 Continuation WO2022249938A1 (ja) 2021-05-28 2022-05-18 ガスタービン燃焼器

Publications (1)

Publication Number Publication Date
US20240085022A1 true US20240085022A1 (en) 2024-03-14

Family

ID=84230055

Family Applications (1)

Application Number Title Priority Date Filing Date
US18/518,811 Pending US20240085022A1 (en) 2021-05-28 2023-11-24 Gas turbine combustor

Country Status (4)

Country Link
US (1) US20240085022A1 (ja)
JP (1) JPWO2022249938A1 (ja)
DE (1) DE112022002817T5 (ja)
WO (1) WO2022249938A1 (ja)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100011770A1 (en) * 2008-07-21 2010-01-21 Ronald James Chila Gas Turbine Premixer with Cratered Fuel Injection Sites
US8955327B2 (en) * 2011-08-16 2015-02-17 General Electric Company Micromixer heat shield
CA2950558C (en) 2014-05-30 2020-10-20 Kawasaki Jukogyo Kabushiki Kaisha Combustor for gas turbine engine
WO2015182727A1 (ja) * 2014-05-30 2015-12-03 川崎重工業株式会社 ガスタービンエンジンの燃焼装置
US10101032B2 (en) * 2015-04-01 2018-10-16 General Electric Company Micromixer system for a turbine system and an associated method thereof
JP2021090376A (ja) 2019-12-10 2021-06-17 佐保 ミドリ 移動式の高踏圧性緑化資材

Also Published As

Publication number Publication date
DE112022002817T5 (de) 2024-03-28
JPWO2022249938A1 (ja) 2022-12-01
WO2022249938A1 (ja) 2022-12-01

Similar Documents

Publication Publication Date Title
US10775047B2 (en) Combustor for gas turbine engine
AU2015268509B2 (en) Combustion device for gas turbine engine
EP2306090B1 (en) Gas turbine combustor
EP2065645B1 (en) Burner and gas turbine combustor
US7669421B2 (en) Combustor of gas turbine with concentric swirler vanes
EP2481986B1 (en) Gas turbine combustor
CA2902809C (en) Lean azimuthal flame combustor
US11365885B2 (en) Gas turbine combustor with fuel injector including a downstream guide member
KR20100080428A (ko) 이중 연료 1차 노즐
US20190360697A1 (en) Fuel injector and gas turbine
JP3903195B2 (ja) 燃料ノズル
US11859822B2 (en) Burner assembly, gas turbine combustor, and gas turbine
JP2018004138A (ja) ガスタービン燃焼器
JPH04103916A (ja) 燃焼装置及びガスタービン装置
US20140007582A1 (en) Gas Turbine Combustor and Operating Method for Gas Turbine Combustor
US9068750B2 (en) Combustor with a pre-nozzle mixing cap assembly
CN111425887B (zh) 燃气轮机燃烧室及燃气轮机
JP2015014400A (ja) ガスタービン燃焼器およびガスタービン燃焼器の燃焼室へ燃料と燃焼用空気を供給する方法
US20240085022A1 (en) Gas turbine combustor
US20220381184A1 (en) Burner assembly, gas turbine combustor, and gas turbine
JP2012098027A (ja) 燃焼器
JP7165545B2 (ja) ガスタービン用燃焼器
WO2023140180A1 (ja) 燃焼器及びガスタービン
JPH05264037A (ja) ガスタービン燃焼器
JPH04198622A (ja) 燃焼器

Legal Events

Date Code Title Description
STPP Information on status: patent application and granting procedure in general

Free format text: DOCKETED NEW CASE - READY FOR EXAMINATION

STPP Information on status: patent application and granting procedure in general

Free format text: NON FINAL ACTION MAILED

AS Assignment

Owner name: KAWASAKI JUKOGYO KABUSHIKI KAISHA, JAPAN

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:KRONIGER, DANIEL;HORIKAWA, ATSUSHI;REEL/FRAME:067297/0924

Effective date: 20240216